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公开(公告)号：US10132330B2
公开(公告)日：2018-11-20
申请号：US15286556
申请日：2016-10-05
Applicant: General Electric Company
Inventor： Prabakaran Modachur Krishnan , Dwight Eric Davidson
Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
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公开(公告)号：US20180094643A1
公开(公告)日：2018-04-05
申请号：US15286545
申请日：2016-10-05
Applicant: General Electric Company
CPC classification number: F04D29/544 , F01D5/141 , F02C3/04 , F04D29/324 , F04D29/384 , F05D2220/32 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/74
Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
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公开(公告)号：US09644483B2
公开(公告)日：2017-05-09
申请号：US13782036
申请日：2013-03-01
Applicant: General Electric Company
Inventor： Moorthi Subramaniyan , Prabakaran Modachur Krishnan
CPC classification number: F01D5/22 , F01D5/143 , F01D5/145 , F01D5/146 , F01D11/001 , F01D11/006 , F01D11/02 , F01D11/08
Abstract: Various embodiments include a turbomachine bucket having a flow interrupter, as well as related turbomachines. Various embodiments include a turbomachine bucket having: a base section sized to couple with a turbomachine rotor, the base section having a leading edge and a trailing edge opposing the leading edge; a blade section coupled to the base section and aligned to extend radially from the base section; a shroud coupled to the blade section and aligned to extend radially from the blade section; and a flow interrupter coupled to the leading edge of the base section.
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公开(公告)号：US10066641B2
公开(公告)日：2018-09-04
申请号：US15286545
申请日：2016-10-05
Applicant: General Electric Company
Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
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公开(公告)号：US20180094644A1
公开(公告)日：2018-04-05
申请号：US15286556
申请日：2016-10-05
Applicant: General Electric Company
Inventor： Prabakaran Modachur Krishnan , Dwight Eric Davidson
CPC classification number: F04D29/544 , F01D5/141 , F02C3/04 , F04D29/324 , F04D29/384 , F05D2220/3216 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/74
Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
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Patent Agency Ranking
公开(公告)号：US09453417B2
公开(公告)日：2016-09-27
申请号：US13633651
申请日：2012-10-02
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Prabakaran Modachur Krishnan , Kevin Joseph Barb , Srikanth Deshpande , Moorthi Subramaniyan
CPC classification number: F01D9/041 , F01D5/143 , F01D5/145 , F01D9/04 , F01D11/08 , F05D2240/125 , F05D2240/126 , Y02E20/16
Abstract: Systems and devices configured to reduce windage and mixing losses in a turbine by redirecting and/or aligning a direction of a leakage flow with the flowpath of the main flow of a turbine are disclosed. In one embodiment, a device includes: a base configured to connect to a diaphragm of a turbine; and a radial portion connected to the base and extending radially inboard from the base toward a rotor of the turbine, the radial portion oriented to adjust a direction of travel of a leakage flow of working fluid radially inboard at an angle complementary to a primary working fluid path of the turbine.
Abstract translation: 公开了通过将泄漏流动的方向与涡轮主流的流路重新导向和/或对准来减少涡轮机中的风阻和混合损失的系统和装置。 在一个实施例中，一种装置包括：基座，其构造成连接到涡轮的隔膜; 以及径向部分，其连接到所述基部并且从所述基部朝向所述涡轮机的转子径向向内延伸，所述径向部分被定向成以与主工作流体互补的角度径向地调节工作流体的泄漏流的行进方向 涡轮机路径。
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公开(公告)号：US20160281518A1
公开(公告)日：2016-09-29
申请号：US15171094
申请日：2016-06-02
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Prabakaran Modachur Krishnan , Kevin Joseph Barb , Srikanth Deshpande , Moorthi Subramaniyan
CPC classification number: F01D9/041 , F01D5/143 , F01D5/145 , F01D9/04 , F01D11/08 , F05D2240/125 , F05D2240/126 , Y02E20/16
Abstract: Systems and devices configured to reduce windage and mixing losses in a turbine by redirecting and/or aligning a direction of a leakage flow with the flowpath of the main flow of a turbine are disclosed. In one embodiment, a device includes: a base configured to connect to a diaphragm of a turbine; and a radial portion connected to the base and extending radially inboard from the base toward a rotor of the turbine, the radial portion oriented to adjust a direction of travel of a leakage flow of working fluid radially inboard at an angle complementary to a primary working fluid path of the turbine.
Abstract translation: 公开了通过将泄漏流动的方向与涡轮主流的流路重新导向和/或对准来减少涡轮机中的风阻和混合损失的系统和装置。 在一个实施例中，一种装置包括：基座，其构造成连接到涡轮的隔膜; 以及径向部分，其连接到所述基部并且从所述基部朝向所述涡轮机的转子径向向内延伸，所述径向部分被定向成以与主工作流体互补的角度径向地调节工作流体的泄漏流的行进方向 涡轮机路径。
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公开(公告)号：US20140248139A1
公开(公告)日：2014-09-04
申请号：US13782036
申请日：2013-03-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Moorthi Subramaniyan , Prabakaran Modachur Krishnan
CPC classification number: F01D5/22 , F01D5/143 , F01D5/145 , F01D5/146 , F01D11/001 , F01D11/006 , F01D11/02 , F01D11/08
Abstract: Various embodiments include a turbomachine bucket having a flow interrupter, as well as related turbomachines. Various embodiments include a turbomachine bucket having: a base section sized to couple with a turbomachine rotor, the base section having a leading edge and a trailing edge opposing the leading edge; a blade section coupled to the base section and aligned to extend radially from the base section; a shroud coupled to the blade section and aligned to extend radially from the blade section; and a flow interrupter coupled to the leading edge of the base section.
Abstract translation: 各种实施例包括具有流动断续器的涡轮机桶以及相关的涡轮机。 各种实施例包括涡轮机桶，其具有：尺寸设计成与涡轮机转子耦合的基部，所述基部具有与前缘相对的前缘和后缘; 叶片部分，其联接到所述基部并且对准以从所述基部径向延伸; 联接到所述叶片部分并对准以从所述叶片部分径向延伸的护罩; 以及联接到基部的前缘的流动断流器。
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公开(公告)号：US20160258295A1
公开(公告)日：2016-09-08
申请号：US14635352
申请日：2015-03-02
Applicant: General Electric Company
Inventor： Moorthi Subramaniyan , Rohit Chouhan , Prabakaran Modachur Krishnan
IPC: F01D5/14
CPC classification number: F01D5/143 , F01D5/145 , F01D11/001 , F05D2220/31 , F05D2220/32 , F05D2240/24 , F05D2240/80 , F05D2260/97
Abstract: Embodiments of the invention relate generally to rotary machines and, more particularly, to the reducing mixing of packing leakage and the main flow of hot gas or steam in gas and steam turbines, respectively. In one embodiment, the invention provides a turbine bucket comprising: a platform portion; an airfoil extending radially outward from the platform portion; and at least one recess extending radially inward into the platform portion, the at least one recess being disposed at an angle relative to a leading edge of the platform portion.
Abstract translation: 本发明的实施方案一般涉及旋转机器，更具体地，涉及分别在气体和蒸汽涡轮机中的填料泄漏和热气体或蒸汽的主流的减少混合。 在一个实施例中，本发明提供一种涡轮机桶，包括：平台部分; 从平台部分径向向外延伸的翼型件; 以及至少一个向内延伸到所述平台部分内的凹部，所述至少一个凹部相对于所述平台部分的前缘以一定角度设置。
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公开(公告)号：US20160201468A1
公开(公告)日：2016-07-14
申请号：US14595321
申请日：2015-01-13
Applicant: General Electric Company
Inventor： Prabakaran Modachur Krishnan , Joseph Anthony Cotroneo
CPC classification number: F01D5/141 , F05D2220/31 , F05D2240/125 , F05D2240/307 , F05D2250/38 , F05D2250/71
Abstract: The present invention is an aerodynamically efficient turbine airfoil that includes a first endwall, a second endwall, a stacking axis, an aspect ratio, a percentage radial span, a tangential offset, and an angle; wherein relationships between the aspect ratio, percentage radial span, and angle are defined.
Abstract translation: 本发明是一种空气动力学有效的涡轮机翼型，其包括第一端壁，第二端壁，堆叠轴，纵横比，径向跨度百分比，切线偏移和角度; 其中定义纵横比，径向百分比和角度之间的关系。
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